[go: up one dir, main page]

US5148670A - Gas turbine cogeneration apparatus for the production of domestic heat and power - Google Patents

Gas turbine cogeneration apparatus for the production of domestic heat and power Download PDF

Info

Publication number
US5148670A
US5148670A US07/727,381 US72738191A US5148670A US 5148670 A US5148670 A US 5148670A US 72738191 A US72738191 A US 72738191A US 5148670 A US5148670 A US 5148670A
Authority
US
United States
Prior art keywords
turbine
air
compressor
combustion
electrical generator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US07/727,381
Inventor
Peter H. Birch
Toshiyuki Kondo
Katsuhiro Mori
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aisin Corp
Original Assignee
Aisin Seiki Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aisin Seiki Co Ltd filed Critical Aisin Seiki Co Ltd
Application granted granted Critical
Publication of US5148670A publication Critical patent/US5148670A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/006—Open cycle gas-turbine in which the working fluid is expanded to a pressure below the atmospheric pressure and then compressed to atmospheric pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/14—Combined heat and power generation [CHP]

Definitions

  • the invention relates to gas turbine apparatus for the generation of electrical power on a domestic scale, preferably with the simultaneous production of heat usable for domestic heating.
  • the simultaneous and in situ generation of heat and electric power (known as cogeneration) on a domestic scale can be advantageous in that a greater total energy efficiency for a particular building and for the nation is possible than when the electrical power is generated centrally for distribution to the building.
  • PCSs low power cogeneration systems
  • the manufacturer of low power PCSs has benefitted from the economies of scale associated with automotive production.
  • PCSs of this type such as that of U.S. Pat. No. 4,226,214, yield total energy efficiencies approaching 90% and can theoretically achieve payback periods of less than three years.
  • the reciprocating engine suffers from at least the following drawbacks; noise and vibration, the need for regular maintenance and lastly, a relatively short operating life.
  • Gas turbine based cogeneration systems currently tend to have larger power outputs, typically at least about one megawatt, and very few companies offer a PCS based on a gas turbine which has a low power rating.
  • Gas turbine PCSs for domestic use are for the present not available because in order to achieve low shaft output powers, conventional gas turbines either must be very small and thus inherently be very high speed devices or must operate under conditions which are not optimum from a design point of view, i.e. on part load. Each of these methods is inherently disadvantageous.
  • the low power implies a small air mass flow rate which dictates the need for miniature components which operate at high speed as a direct result of increasing pressure ratio and density.
  • Such small components theoretically have high efficiencies but in practice constructional tolerances and operating clearances diminish the thermodynamic performance.
  • Part load operation of gas turbines in general requires a reduced turbine entry temperature and lower pressure ratios which, by the laws of thermodynamics, results in a lower brake power thermal efficiency.
  • a further disadvantage of conventional gas turbines is the high combustion pressure which necessitates a higher fuel pressure.
  • the requirement to pressurize the fuel results in the output shaft power being negated by the amount of work necessary to pressurize the fuel, further decreasing the brake power thermal efficiencies.
  • provision must be made in the plant for pressurizing the fuel which necessitates additional space requirements and expense.
  • a gas turbine based PCS has the advantages of reduced maintenance, greater design life and reduced noise and vibration, making it compatible with the intended environment.
  • An object of this invention is the production of electrical power in a range from less than 1 kW up to 10 Kw, advantageously together with heat energy in the form of hot water, substantially for the purpose of domestic scale use.
  • the invention provides an apparatus for the domestic production of electricity, advantageously conjointly with usable heat, comprising:
  • At least one turbine in which the gaseous combustion gases are expanded and perform work, the turbine or turbines being connected to drive a compressor and an electrical generator;
  • a gas turbine engine which operates on an inverted Brayton cycle.
  • the component configurations are depicted in FIG. 1 and FIG. 2. Inversion of the Brayton cycle for the production of low shaft powers creates specific advantages when compared with conventional gas turbines while retaining the favorable characteristics and features that make a turbine preferable to a reciprocating engine for the purpose of producing combined heat and power for domestic use.
  • the invention provides a PCS which operates on an inverted Brayton cycle. That is to say, during the cycle the pressure is reduced rather than increased as is conventional.
  • the gas turbine engine drives an electric generator for the production of electrical power.
  • Heat recovery is effected by the placement of a heat exchanger in the exhaust stream of the engine.
  • An important feature of this invention is the effect of inverting the Brayton cycle and the consequent change in working fluid density.
  • Working fluid density has a major influence on the design of efficient turbines and compressors.
  • a conventional gas turbine engine designed for low power duties has miniature sized components operating at very high speed. This is a consequence of the working fluid density increasing in the normal way.
  • These miniature components can be designed theoretically to be efficient but unfortunately in practice the effect of constructional tolerances and operating component clearances usually negate their performance.
  • Inversion of the Brayton cycle means that the machine operates at a pressure below atmospheric.
  • the consequent reduction in working fluid density increases the size of the machine.
  • This is a feature which completely opposes the basic advantage of a normal Brayton cycle gas turbine which is a high working fluid density machine.
  • the turbines and compressors can be designed and constructed with the advantages of conventional size, conventional materials and conventional rotational speeds.
  • the design and use of radial turbines and centrifugal compressors in the apparatus of this invention occurs substantially at the thermodynamic optimum resulting in geometries which have high efficiencies.
  • Another advantage of this system is the elimination of a fuel pump or fuel compressor. This is a result of combustion occurring at or just below atmospheric pressure. The output power is as a consequence not negated, as it is in a normal gas turbine, by the need to pressurize the fuel with independent equipment.
  • Starting of the apparatus may be effected with a simple air blower connected for the duration of the start sequence to the air intake of the gas turbine.
  • the air blower creates a higher pressure difference across the turbine than the compressor. This allows the turbine to do work on the compressor, and accelerates the rotation of the shaft, sufficient for a successful start.
  • FIG. 1 shows a schematic view of an inverted Brayton cycle PCS having a gas single shaft turbine, together with the equipment necessary to start the engine and recover the electrical and thermal energy;
  • FIG. 2 shows a schematic view of an inverted Brayton cycle PCS having two shaft gas turbines together with the equipment necessary to start the engine and recover the electrical and thermal energy.
  • FIG. 1 there is shown an inverted Brayton cycle gas turbine engine interfaced with that equipment necessary to produce heat in the form of hot water and electrical power. Not shown is a control unit of the analog or digital type which detects the installation heat and electrical power demands and operates the gas turbine engine as appropriate.
  • the cycle working fluid is air, the air path being as follows: In normal operation, combustion air is drawn through a flap valve 2. It passes through an air filter 3 and into a cycle heat exchanger 4. It then passes into a combustion chamber 6 where fuel is admitted by a fuel control valve 5 and combusted. The hot combustion gases expand through a turbine 7 which may be radial or axial in design. The combustion gases then pass into the above mentioned heat exchanger 4 where they heat the incoming air and are cooled in the process. The cooled combustion gases are then recompressed to substantially atmospheric pressure in a compressor 8 which may be of the centrifugal-type. The gases after compression are at a temperature higher than ambient and are then passed through another heat exchanger, namely a domestic heat recovery unit 11, which can comprise a gas-to-water heat exchanger, for example.
  • a domestic heat recovery unit 11 which can comprise a gas-to-water heat exchanger, for example.
  • a small electrically operated blower 1 forces air past the flap valve 2 and through the engine as previously described.
  • the air supply is sufficient to combust with the fuel and start the engine.
  • the expansion turbine 7 is connected via a shaft to the compressor 8 and an electric generator 9.
  • the shaft is supported in bearings which resist radial and axial movement.
  • the generator 9 can comprise an alternator, for example, and the compressor 8 can comprise a centrifugal compressor for example.
  • the electrical power output from the electrical generator 9 is conditioned by appropriate equipment 10 such as a frequency converter for supplying electricity to a domestic electrical supply source such as a main power supply.
  • FIG. 2 depicts a two turbine design.
  • the mode of operation is the same as that previously described except that instead of the turbine 12 driving both the compressor 8 and the generator 9, a second turbine 13, driving the electrical generator 9, is placed in the hot air stream before the heat exchanger 4 and after the turbine 12 which drives the compressor 8.
  • a useful and desirable feature, not illustrated in the drawings, is for all of the equipment to be encased in a thermally and acoustically sealed unit thus enhancing the overall appearance and specification.
  • the invention overcomes the normal disadvantages of conventional gas turbines. However, this is achieved while still retaining a simple construction and an inherently long design life. Noise and vibration can also be virtually eliminated making the invention a superior choice as compared with reciprocating engines designed for the same duty.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Eletrric Generators (AREA)

Abstract

An apparatus for the domestic cogeneration of heat and electrical energy utilizing an inverted Brayton cycle gas turbine, a combustion chamber, an electrical generator and a compressor. Combustion air is preheated in a heat exchanger by gaseous combustion gases or exhaust gases exiting from the turbine. The combustion air is supplied at substantially atmospheric pressure to the combustion chamber where fuel is burned. The cooled gaseous combustion gases exiting from the heat exchanger are then fed to the compressor where they are recompressed to atmospheric pressure, and are finally used to heat the working fluid of a domestic heating system before being exhausted to the atmosphere. The apparatus can also include an acoustically and thermally insulated housing, an electric air blower for start-up, an engine ignition device, a frequency converter which conditions the electric generator output for connection to the main supply and a control system which is cooled by the engine intake air and which detects thermal and electrical demand and adjusts the engine power accordingly.

Description

This application is a continuation of application Ser. No. 07/330,275, filed Mar. 29, 1989 now abandoned.
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to gas turbine apparatus for the generation of electrical power on a domestic scale, preferably with the simultaneous production of heat usable for domestic heating.
The simultaneous and in situ generation of heat and electric power (known as cogeneration) on a domestic scale can be advantageous in that a greater total energy efficiency for a particular building and for the nation is possible than when the electrical power is generated centrally for distribution to the building.
Legislation in most countries now permits and encourages private generation of electrical power especially for combined heat and power projects. This legislation also allows private generators to operate electrical generating equipment in parallel with the main supply.
Currently the smallest commercial cogeneration equipment available has an electrical power rating of approximately 15 kW. In general, packaged cogeneration equipment of this size is too large for domestic use where electrical power ratings of approximately 1 kW would be more appropriate.
2. Description of the Related Art
To date, low power cogeneration systems (PCSs) have almost exclusively been based on reciprocating engines of the automotive type and converted in most cases to run on fuels such as natural gas. The manufacturer of low power PCSs has benefitted from the economies of scale associated with automotive production. PCSs of this type, such as that of U.S. Pat. No. 4,226,214, yield total energy efficiencies approaching 90% and can theoretically achieve payback periods of less than three years.
However, in small scale applications such as a domestic combined heat and power unit, the reciprocating engine suffers from at least the following drawbacks; noise and vibration, the need for regular maintenance and lastly, a relatively short operating life.
Gas turbine based cogeneration systems currently tend to have larger power outputs, typically at least about one megawatt, and very few companies offer a PCS based on a gas turbine which has a low power rating.
Gas turbine PCSs for domestic use are for the present not available because in order to achieve low shaft output powers, conventional gas turbines either must be very small and thus inherently be very high speed devices or must operate under conditions which are not optimum from a design point of view, i.e. on part load. Each of these methods is inherently disadvantageous.
In the first instance, the low power implies a small air mass flow rate which dictates the need for miniature components which operate at high speed as a direct result of increasing pressure ratio and density. Such small components theoretically have high efficiencies but in practice constructional tolerances and operating clearances diminish the thermodynamic performance. Part load operation of gas turbines in general requires a reduced turbine entry temperature and lower pressure ratios which, by the laws of thermodynamics, results in a lower brake power thermal efficiency.
Mechanical losses will account for proportionally more of the shaft output power as a larger machine is operated at part load, reducing the brake power thermal efficiencies still further.
A further disadvantage of conventional gas turbines is the high combustion pressure which necessitates a higher fuel pressure. The requirement to pressurize the fuel results in the output shaft power being negated by the amount of work necessary to pressurize the fuel, further decreasing the brake power thermal efficiencies. Also, provision must be made in the plant for pressurizing the fuel which necessitates additional space requirements and expense. However, in the domestic situation a gas turbine based PCS has the advantages of reduced maintenance, greater design life and reduced noise and vibration, making it compatible with the intended environment.
SUMMARY OF THE INVENTION
An object of this invention is the production of electrical power in a range from less than 1 kW up to 10 Kw, advantageously together with heat energy in the form of hot water, substantially for the purpose of domestic scale use.
The invention provides an apparatus for the domestic production of electricity, advantageously conjointly with usable heat, comprising:
a heat exchanger in which combustion air is preheated;
a combustion chamber in which fuel is burned in the preheated combustion air to form gaseous combustion gases;
at least one turbine in which the gaseous combustion gases are expanded and perform work, the turbine or turbines being connected to drive a compressor and an electrical generator; and
means for passing the gaseous combustion gases from the turbine or turbines through the heat exchanger to preheat combustion air and hence to the compressor for recompression.
In a preferred embodiment, a gas turbine engine is utilized which operates on an inverted Brayton cycle. The component configurations are depicted in FIG. 1 and FIG. 2. Inversion of the Brayton cycle for the production of low shaft powers creates specific advantages when compared with conventional gas turbines while retaining the favorable characteristics and features that make a turbine preferable to a reciprocating engine for the purpose of producing combined heat and power for domestic use.
In the preferred embodiment, the invention provides a PCS which operates on an inverted Brayton cycle. That is to say, during the cycle the pressure is reduced rather than increased as is conventional. The gas turbine engine drives an electric generator for the production of electrical power. Heat recovery is effected by the placement of a heat exchanger in the exhaust stream of the engine. By this means, effective use of an original energy source such as liquid or gaseous fuel is sought.
An important feature of this invention is the effect of inverting the Brayton cycle and the consequent change in working fluid density. Working fluid density has a major influence on the design of efficient turbines and compressors. A conventional gas turbine engine designed for low power duties has miniature sized components operating at very high speed. This is a consequence of the working fluid density increasing in the normal way. These miniature components can be designed theoretically to be efficient but unfortunately in practice the effect of constructional tolerances and operating component clearances usually negate their performance.
Inversion of the Brayton cycle means that the machine operates at a pressure below atmospheric. The consequent reduction in working fluid density increases the size of the machine. This is a feature which completely opposes the basic advantage of a normal Brayton cycle gas turbine which is a high working fluid density machine. However, in this case where low power is required, the turbines and compressors can be designed and constructed with the advantages of conventional size, conventional materials and conventional rotational speeds.
The aforementioned features of the invention create the added advantage that current manufacturing techniques such as those utilized in the production of turbochargers can be applied with consequent economies in manufacture. Also, in recent times these components have become very efficient and this feature enables conventional automotive turbocharger design techniques to be applied to the invention.
For low power requirements such as those envisaged for the domestic cogeneration system, the design and use of radial turbines and centrifugal compressors in the apparatus of this invention occurs substantially at the thermodynamic optimum resulting in geometries which have high efficiencies.
Another advantage of this system is the elimination of a fuel pump or fuel compressor. This is a result of combustion occurring at or just below atmospheric pressure. The output power is as a consequence not negated, as it is in a normal gas turbine, by the need to pressurize the fuel with independent equipment.
Starting of the apparatus may be effected with a simple air blower connected for the duration of the start sequence to the air intake of the gas turbine. The air blower creates a higher pressure difference across the turbine than the compressor. This allows the turbine to do work on the compressor, and accelerates the rotation of the shaft, sufficient for a successful start.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will now be described with reference to the accompanying drawings, in which:
FIG. 1 shows a schematic view of an inverted Brayton cycle PCS having a gas single shaft turbine, together with the equipment necessary to start the engine and recover the electrical and thermal energy; and
FIG. 2 shows a schematic view of an inverted Brayton cycle PCS having two shaft gas turbines together with the equipment necessary to start the engine and recover the electrical and thermal energy.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
In FIG. 1 there is shown an inverted Brayton cycle gas turbine engine interfaced with that equipment necessary to produce heat in the form of hot water and electrical power. Not shown is a control unit of the analog or digital type which detects the installation heat and electrical power demands and operates the gas turbine engine as appropriate.
The cycle working fluid is air, the air path being as follows: In normal operation, combustion air is drawn through a flap valve 2. It passes through an air filter 3 and into a cycle heat exchanger 4. It then passes into a combustion chamber 6 where fuel is admitted by a fuel control valve 5 and combusted. The hot combustion gases expand through a turbine 7 which may be radial or axial in design. The combustion gases then pass into the above mentioned heat exchanger 4 where they heat the incoming air and are cooled in the process. The cooled combustion gases are then recompressed to substantially atmospheric pressure in a compressor 8 which may be of the centrifugal-type. The gases after compression are at a temperature higher than ambient and are then passed through another heat exchanger, namely a domestic heat recovery unit 11, which can comprise a gas-to-water heat exchanger, for example.
In the starting condition a small electrically operated blower 1 forces air past the flap valve 2 and through the engine as previously described. The air supply is sufficient to combust with the fuel and start the engine.
Each item in the air/gas path is joined with appropriate duct work.
The expansion turbine 7 is connected via a shaft to the compressor 8 and an electric generator 9. The shaft is supported in bearings which resist radial and axial movement. The generator 9 can comprise an alternator, for example, and the compressor 8 can comprise a centrifugal compressor for example.
The electrical power output from the electrical generator 9 is conditioned by appropriate equipment 10 such as a frequency converter for supplying electricity to a domestic electrical supply source such as a main power supply.
FIG. 2 depicts a two turbine design. The mode of operation is the same as that previously described except that instead of the turbine 12 driving both the compressor 8 and the generator 9, a second turbine 13, driving the electrical generator 9, is placed in the hot air stream before the heat exchanger 4 and after the turbine 12 which drives the compressor 8.
A useful and desirable feature, not illustrated in the drawings, is for all of the equipment to be encased in a thermally and acoustically sealed unit thus enhancing the overall appearance and specification.
The invention overcomes the normal disadvantages of conventional gas turbines. However, this is achieved while still retaining a simple construction and an inherently long design life. Noise and vibration can also be virtually eliminated making the invention a superior choice as compared with reciprocating engines designed for the same duty.
While the present invention has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes and modifications may be made thereto which fall within the scope of the appended claims.

Claims (13)

What is claimed is:
1. An apparatus for the domestic production of electricity, comprising:
a normal air intake for supplying atmospheric air as combustion air,
a heat exchanger in which combustion air is preheated;
means for supplying non-pressurized fuel,
a combustion chamber in which the non-pressurized fuel is burned in the preheated combustion air at a pressure no greater than atmospheric pressure to form gaseous combustion gases;
a centrifugal compressor;
an electrical generator;
at least one radial turbine in which the gaseous combustion gases are expanded and do work, the at least one turbine being connected to drive the compressor and said electrical generator;
means for starting the apparatus including an electric air blower and a valve which automatically closes the normal air intake during start up, for drawing air from the atmosphere and delivering it through the heat exchanger and combustion chamber to the turbine inlet; and
means for passing the gaseous combustion gases from said at least one turbine through said heat exchanger to preheat the combustion air and then to said compressor for recompression.
2. The apparatus according to claim 1, wherein said electrical generator is an alternator.
3. The apparatus according to claim 1, further comprising electrical conditioning equipment for conditioning electrical output of said electrical generator to be suitable for connection to a domestic electrical supply source.
4. The apparatus according to claim 1, further comprising a fuel control valve for controlling the rate of supply of fuel to said combustion chamber.
5. The apparatus according to claim 1, in which said at least one turbine comprises a single turbine which drives both said compressor and said electrical generator.
6. The apparatus according to claim 1, wherein said at least one turbine comprises two turbines, a first one of the turbines driving the compressor and a second one of said turbines driving said electrical generator, the gaseous combustion gases passing through the first and second turbines sequentially.
7. An apparatus for the domestic cogeneration of heat and electricity, comprising:
a normal air intake for supplying atmospheric air as combustion air,
a heat exchanger in which the combustion air is preheated;
means for supplying non-pressurized fuel,
a combustion chamber in which the non-pressurized fuel is burned in the preheated combustion air at a pressure no greater than atmospheric pressure to form gaseous combustion gases;
a centrifugal compressor;
an electrical generator;
at least one radial turbine in which the gaseous combustion gases are expanded and do work, the at least one turbine being connected to drive the compressor and said electrical generator;
means for starting the apparatus including an electric air blower for drawing air from the atmosphere and delivering it through the heat exchanger and combustion chamber to the turbine inlet air via a valve which automatically closes the normal air intake during start-up;
means for passing the low density gaseous combustion gases from said at least one turbine through said heat exchanger to preheat the combustion air and then to said compressor for recompression; and
means for extracting residual heat from the recompressed gaseous combustion gases.
8. The apparatus according to claim 7, wherein said means for extracting residual heat from the recompressed gaseous combustion gases comprises a gas-to-water heat exchanger.
9. The apparatus according to claim 2, wherein said electrical generator is an alternator.
10. The apparatus according to claim 7, further comprising electrical conditioning equipment for conditioning electrical output of said electrical generator to be suitable for connection to a domestic electrical supply source.
11. The apparatus according to claim 7, further comprising a fuel control valve for controlling the rate of supply of fuel to said combustion chamber.
12. The apparatus according to claim 7, in which said at least one turbine comprises a single turbine which drives both said compressor and said electrical generator.
13. The apparatus according to claim 7, wherein said at least one turbine comprises two turbines, a first one of said turbines driving said compressor and a second one of said turbines driving said electrical generator, the gaseous combustion gases passing through the first and second turbines sequentially.
US07/727,381 1988-03-31 1991-07-05 Gas turbine cogeneration apparatus for the production of domestic heat and power Expired - Fee Related US5148670A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8807664A GB2216191B (en) 1988-03-31 1988-03-31 Gas turbine cogeneration apparatus for the production of domestic heat and power
GB8807664 1988-03-31

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
US07330275 Continuation 1989-03-29

Publications (1)

Publication Number Publication Date
US5148670A true US5148670A (en) 1992-09-22

Family

ID=10634412

Family Applications (1)

Application Number Title Priority Date Filing Date
US07/727,381 Expired - Fee Related US5148670A (en) 1988-03-31 1991-07-05 Gas turbine cogeneration apparatus for the production of domestic heat and power

Country Status (3)

Country Link
US (1) US5148670A (en)
JP (1) JPH01280638A (en)
GB (1) GB2216191B (en)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5819524A (en) * 1996-10-16 1998-10-13 Capstone Turbine Corporation Gaseous fuel compression and control system and method
WO1999004170A1 (en) * 1997-07-14 1999-01-28 Ge Energy Products Germany Gmbh Gas turbine and method for operating the same
US6044640A (en) * 1995-08-09 2000-04-04 Guimaraes; Edison Tito Process and installation for cooling air
EP1057986A1 (en) * 1998-12-21 2000-12-06 Japan Science and Technology Corporation Heat engine
WO2001018371A1 (en) * 1999-09-07 2001-03-15 Geza Vermes Ambient pressure gas turbine system
WO2001063175A2 (en) * 2000-02-23 2001-08-30 Honeywell International Inc. Reversible recuperator
US6363708B1 (en) * 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) * 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6438936B1 (en) 2000-05-16 2002-08-27 Elliott Energy Systems, Inc. Recuperator for use with turbine/turbo-alternator
US6442945B1 (en) * 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US6460324B1 (en) * 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
WO2002095768A1 (en) * 2001-05-25 2002-11-28 Pebble Bed Modular Reactor (Proprietary) Limited A brayton cycle nuclear power plant and a method of starting the brayton cycle
US6526757B2 (en) * 2001-02-13 2003-03-04 Robin Mackay Multi pressure mode gas turbine
US6546736B2 (en) * 1998-09-25 2003-04-15 Alm Development, Inc. Method of operation of gas turbine engine
US6606864B2 (en) * 2001-02-13 2003-08-19 Robin Mackay Advanced multi pressure mode gas turbine
WO2004057170A1 (en) * 2002-12-23 2004-07-08 Turbec Ab Gas turbine power plant
US20040146135A1 (en) * 2001-05-23 2004-07-29 Frank Curtolo Device for slowing down spherical elements in a pebble bed nuclear reactor
US20050074083A1 (en) * 2000-09-04 2005-04-07 Haasbroek Andries Cornelius Nuclear reactor
US20060162316A1 (en) * 2002-10-08 2006-07-27 Kawasaki Jokogyo Kabushiki Kaisha Atmospheric pressure combustion turbine system
US20060248899A1 (en) * 2003-02-11 2006-11-09 Uwe Borchert Method for producing gas turbines and gas turbine assembly
US20070044480A1 (en) * 2005-08-25 2007-03-01 Lennox Manufacturing Inc. Combined apparatus for fluid heating and electrical power generation
US7275395B1 (en) 2004-09-15 2007-10-02 Ventura Entreprises Method and apparatus for making dry ice
US20070261826A1 (en) * 2004-09-16 2007-11-15 Holmen Hans K Method and a System for Energy Recovery and/or Cooling
US20100031669A1 (en) * 2008-08-06 2010-02-11 Cessna Aircraft Company Free Turbine Generator For Aircraft
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
DE102013100342A1 (en) 2013-01-14 2014-07-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Gas turbine device for use in mini block-type thermal power station, has liquid-gas heat exchangers for transferring heat of exhaust gas from turbine to transmission liquid, before supply of exhaust gas to compression device
US20160319749A1 (en) * 2015-04-29 2016-11-03 Alstom Technology Ltd Control concept for closed loop brayton cycle
WO2021025986A1 (en) * 2019-08-02 2021-02-11 Dynamo Micropower Corporation Gas turbine heater and dual fuel gas turbine engine
US10934894B2 (en) 2015-12-11 2021-03-02 Hieta Technologies Limited Inverted brayton cycle heat engine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2236808B (en) * 1989-08-19 1994-05-11 James Gavin Warnock Energy storage/transfer system
GB2298238A (en) * 1995-02-21 1996-08-28 Mark John Snee Radial turbine and compressor arrangements
RU2093415C1 (en) * 1996-07-05 1997-10-20 Йелстаун Корпорейшн Н.В. Heat generator for montgolfier
GB2351776A (en) * 1999-07-03 2001-01-10 Rolls Royce Plc A gas turbine engine
JP4619563B2 (en) * 2001-02-20 2011-01-26 昭一 藤井 Ultra turbine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612237A (en) * 1945-05-22 1948-11-10 Bbc Brown Boveri & Cie Improvements in or relating to gas turbine plants
GB651166A (en) * 1947-07-21 1951-03-14 Rateau Soc Improvements in or relating to gas turbine plant with semi-open circuit
US3369361A (en) * 1966-03-07 1968-02-20 Gale M. Craig Gas turbine power plant with sub-atmospheric spray-cooled turbine discharge into exhaust compressor
US3487482A (en) * 1967-11-29 1970-01-06 Evans Chandler Inc Fuel control
GB1442367A (en) * 1973-01-25 1976-07-14 Siemens Ag Gas turbine engines
US4154055A (en) * 1977-03-25 1979-05-15 Ford Motor Company Indirect Brayton energy recovery system
WO1981000878A1 (en) * 1979-09-28 1981-04-02 Mo V G P Inst Steam-and-gas turbine plant
US4414805A (en) * 1981-11-27 1983-11-15 General Motors Corporation Hybrid gas turbine engine and flywheel propulsion system
US4502277A (en) * 1984-01-25 1985-03-05 Demos Papastavros Turbine power plant system
US4875436A (en) * 1988-02-09 1989-10-24 W. R. Grace & Co.-Conn. Waste heat recovery system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS594866A (en) * 1982-06-29 1984-01-11 株式会社島津製作所 Thermal energy utilizing system
US4529887A (en) * 1983-06-20 1985-07-16 General Electric Company Rapid power response turbine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612237A (en) * 1945-05-22 1948-11-10 Bbc Brown Boveri & Cie Improvements in or relating to gas turbine plants
GB651166A (en) * 1947-07-21 1951-03-14 Rateau Soc Improvements in or relating to gas turbine plant with semi-open circuit
US3369361A (en) * 1966-03-07 1968-02-20 Gale M. Craig Gas turbine power plant with sub-atmospheric spray-cooled turbine discharge into exhaust compressor
US3487482A (en) * 1967-11-29 1970-01-06 Evans Chandler Inc Fuel control
GB1442367A (en) * 1973-01-25 1976-07-14 Siemens Ag Gas turbine engines
US4154055A (en) * 1977-03-25 1979-05-15 Ford Motor Company Indirect Brayton energy recovery system
WO1981000878A1 (en) * 1979-09-28 1981-04-02 Mo V G P Inst Steam-and-gas turbine plant
US4414805A (en) * 1981-11-27 1983-11-15 General Motors Corporation Hybrid gas turbine engine and flywheel propulsion system
US4502277A (en) * 1984-01-25 1985-03-05 Demos Papastavros Turbine power plant system
US4875436A (en) * 1988-02-09 1989-10-24 W. R. Grace & Co.-Conn. Waste heat recovery system

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6044640A (en) * 1995-08-09 2000-04-04 Guimaraes; Edison Tito Process and installation for cooling air
US5850733A (en) * 1996-10-16 1998-12-22 Capstone Turbine Corporation Gaseous fuel compression and control system and method
US5819524A (en) * 1996-10-16 1998-10-13 Capstone Turbine Corporation Gaseous fuel compression and control system and method
WO1999004170A1 (en) * 1997-07-14 1999-01-28 Ge Energy Products Germany Gmbh Gas turbine and method for operating the same
WO1999004169A1 (en) * 1997-07-14 1999-01-28 Ge Energy Products Germany Gmbh Method and device for compressing an industrial gas
US6546736B2 (en) * 1998-09-25 2003-04-15 Alm Development, Inc. Method of operation of gas turbine engine
US6557337B1 (en) * 1998-09-25 2003-05-06 Alm Development, Inc. Gas turbine engine
EP1057986A1 (en) * 1998-12-21 2000-12-06 Japan Science and Technology Corporation Heat engine
EP1057986A4 (en) * 1998-12-21 2005-10-19 Japan Science & Tech Agency THERMAL MOTOR
WO2001018371A1 (en) * 1999-09-07 2001-03-15 Geza Vermes Ambient pressure gas turbine system
US6298654B1 (en) 1999-09-07 2001-10-09 VERMES GéZA Ambient pressure gas turbine system
US6460324B1 (en) * 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
US6363708B1 (en) * 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) * 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
WO2001063175A3 (en) * 2000-02-23 2002-02-28 Honeywell Int Inc Reversible recuperator
WO2001063175A2 (en) * 2000-02-23 2001-08-30 Honeywell International Inc. Reversible recuperator
US6837419B2 (en) 2000-05-16 2005-01-04 Elliott Energy Systems, Inc. Recuperator for use with turbine/turbo-alternator
US6438936B1 (en) 2000-05-16 2002-08-27 Elliott Energy Systems, Inc. Recuperator for use with turbine/turbo-alternator
US6442945B1 (en) * 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US20050074083A1 (en) * 2000-09-04 2005-04-07 Haasbroek Andries Cornelius Nuclear reactor
US6526757B2 (en) * 2001-02-13 2003-03-04 Robin Mackay Multi pressure mode gas turbine
US6606864B2 (en) * 2001-02-13 2003-08-19 Robin Mackay Advanced multi pressure mode gas turbine
US20040146135A1 (en) * 2001-05-23 2004-07-29 Frank Curtolo Device for slowing down spherical elements in a pebble bed nuclear reactor
WO2002095768A1 (en) * 2001-05-25 2002-11-28 Pebble Bed Modular Reactor (Proprietary) Limited A brayton cycle nuclear power plant and a method of starting the brayton cycle
US20040131138A1 (en) * 2001-05-25 2004-07-08 Michael Correia Brayton cycle nuclear power plant and a method of starting the brayton cycle
US7204077B2 (en) * 2002-10-08 2007-04-17 Kawasaki Jukogyo Kabushiki Kaisha Atmospheric pressure combustion turbine system
US20060162316A1 (en) * 2002-10-08 2006-07-27 Kawasaki Jokogyo Kabushiki Kaisha Atmospheric pressure combustion turbine system
WO2004057170A1 (en) * 2002-12-23 2004-07-08 Turbec Ab Gas turbine power plant
US20060248899A1 (en) * 2003-02-11 2006-11-09 Uwe Borchert Method for producing gas turbines and gas turbine assembly
US7275395B1 (en) 2004-09-15 2007-10-02 Ventura Entreprises Method and apparatus for making dry ice
US20070261826A1 (en) * 2004-09-16 2007-11-15 Holmen Hans K Method and a System for Energy Recovery and/or Cooling
US20070044480A1 (en) * 2005-08-25 2007-03-01 Lennox Manufacturing Inc. Combined apparatus for fluid heating and electrical power generation
US7647762B2 (en) 2005-08-25 2010-01-19 Lennox Industries Inc. Combined apparatus for fluid heating and electrical power generation
US20100031669A1 (en) * 2008-08-06 2010-02-11 Cessna Aircraft Company Free Turbine Generator For Aircraft
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
US8689561B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Vortex premixer for combustion apparatus
DE102013100342A1 (en) 2013-01-14 2014-07-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Gas turbine device for use in mini block-type thermal power station, has liquid-gas heat exchangers for transferring heat of exhaust gas from turbine to transmission liquid, before supply of exhaust gas to compression device
US20160319749A1 (en) * 2015-04-29 2016-11-03 Alstom Technology Ltd Control concept for closed loop brayton cycle
US10001065B2 (en) * 2015-04-29 2018-06-19 General Electric Technology Gmbh Control concept for closed loop Brayton cycle
US10934894B2 (en) 2015-12-11 2021-03-02 Hieta Technologies Limited Inverted brayton cycle heat engine
WO2021025986A1 (en) * 2019-08-02 2021-02-11 Dynamo Micropower Corporation Gas turbine heater and dual fuel gas turbine engine

Also Published As

Publication number Publication date
JPH01280638A (en) 1989-11-10
GB2216191A (en) 1989-10-04
GB8807664D0 (en) 1988-05-05
GB2216191B (en) 1992-08-12

Similar Documents

Publication Publication Date Title
US5148670A (en) Gas turbine cogeneration apparatus for the production of domestic heat and power
US6079197A (en) High temperature compression and reheat gas turbine cycle and related method
US6003298A (en) Steam driven variable speed booster compressor for gas turbine
JP3162479B2 (en) Gas / steam combined power plant
US6892542B2 (en) Gas compression system and method for microturbine application
US6170251B1 (en) Single shaft microturbine power generating system including turbocompressor and auxiliary recuperator
KR100788322B1 (en) A microturbine power generating system and a method thereof
US5799484A (en) Dual turbogenerator auxiliary power system
US6363706B1 (en) Apparatus and method to increase turbine power
EP0271360A2 (en) Power generating device and method
WO1994025746A1 (en) High efficiency multi-shaft reheat turbine with intercooling and recuperation
US6735953B1 (en) Turbomachine-driven environmental control system
US7299638B2 (en) Combined heat and power system
US6032459A (en) Turbine exhaust cooling in a microturbine power generating system
US3394265A (en) Spinning reserve with inlet throttling and compressor recirculation
US6418707B1 (en) General advanced power system
JPH0949436A (en) Starting method of combination plant
US6751940B1 (en) High efficiency gas turbine power generator
JPH07332109A (en) Compressed air storage type power generating plant
EP0811752A1 (en) Centrifugal gas turbine
US2730863A (en) Gaseous fuel turbine power plant having parallel connected compressors
GB2283064A (en) Internal combustion engine exhaust gas energy recovery
RU2192551C2 (en) Gas turbine engine with regeneration of heat
RU2111370C1 (en) Method of starting and gas supply of power generating gas turbine plant
GB2126658A (en) Generation of power from liquid hydrogen

Legal Events

Date Code Title Description
FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

FPAY Fee payment

Year of fee payment: 4

REMI Maintenance fee reminder mailed
LAPS Lapse for failure to pay maintenance fees
STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362